CN210652213U - Needle-punched non-woven fabric composite board for aircraft interior trim panel - Google Patents
Needle-punched non-woven fabric composite board for aircraft interior trim panel Download PDFInfo
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- CN210652213U CN210652213U CN201921540752.1U CN201921540752U CN210652213U CN 210652213 U CN210652213 U CN 210652213U CN 201921540752 U CN201921540752 U CN 201921540752U CN 210652213 U CN210652213 U CN 210652213U
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Abstract
The utility model discloses a needle-punched non-woven fabric composite board for an aircraft interior trim panel, which comprises at least one layer of a surface covering layer and a needle-punched non-woven fabric layer which is hot-pressed with the surface covering layer; the needle-punched non-woven fabric layer is formed by needle-punching a flame-retardant layer and a reinforcing layer, and the flame-retardant layer is combined with the sealing surface layer in a hot-pressing mode. The utility model discloses a composite sheet has good gas permeability, sound absorption and heat insulation, fire behaviour and high strength. Use the utility model discloses the travelling comfort that can promote the passenger and sit the aircraft in the plaque is arranged in the aircraft interior to the preparation, and noise reduction improves the security.
Description
Technical Field
The utility model relates to a combined material field especially relates to plaque is with acupuncture non-woven fabrics composite sheet in aircraft.
Background
With the continuous improvement of the living standard of people, the travel becomes an indispensable rhythm. With the attention of people on traveling, transportation tools which are safe, convenient, fast and comfortable to travel are often selected, so that the airplane becomes one of the necessary choices, and various discomforts caused by the traffic can be effectively shortened. The interior trim panel of the airplane needs to meet the requirements of light weight, high strength, sound absorption and heat insulation. At present, the common aircraft cabin interior trim panel structure is a honeycomb sandwich structure formed by gluing a non-metal honeycomb core material and a composite material panel, and a decorative film is laid on the panel. The composite board is mostly high-strength boards such as aramid fiber boards and carbon fiber boards, but the heat insulation capability is very small, and the interior structure can not meet the requirements of heat insulation and noise reduction of people in an airplane cabin. The composite board with good heat insulation and sound absorption effects is lack of flame retardant effect. The breathability of the panel that meets all of the above requirements is difficult to achieve. The composite board prepared by the needle-punched non-woven fabric can improve the air permeability of the material, and meanwhile, the needle-punched non-woven fabric contains a large number of micro pores, which is beneficial to sound absorption and heat insulation.
The needle-punched non-woven fabric is made of fiber material and through several times of needle punching and proper hot rolling. The needled non-woven fabric has good air permeability and certain sound absorption and heat insulation functions, and the composite board can be prepared by compounding and preheating the needled non-woven fabric or felt and other materials and then putting the preheated needled non-woven fabric or felt into a die for compression molding in the prior art. In patent CN 103302864B, "a natural fiber and polylactic acid fiber blended fiber board and its preparation method" and patent CN 109334146a, "a production method of natural bamboo fiber composite board", both of them use needle-punched non-woven fabric as composite board, but both of them do not have flame retardant effect and general heat insulation effect. Therefore, a needled non-woven fabric composite board which is good in air permeability, sound-absorbing and heat-insulating, flame-retardant and high in strength is needed.
SUMMERY OF THE UTILITY MODEL
The utility model discloses to prior art's not enough, it is good to provide a gas permeability, and the sound absorption is thermal-insulated has the acupuncture non-woven fabrics composite sheet that flame retardant efficiency and intensity are high.
The utility model is realized through the following technical scheme, the utility model provides an aircraft interior plaque with acupuncture non-woven fabrics composite sheet in a first aspect, the composite sheet includes at least one deck facing layer, still includes the acupuncture non-woven fabrics layer that bonds with the facing layer; the needle-punched non-woven fabric layer is formed by needle punching a flame-retardant layer and a reinforcing layer; and the flame-retardant layer is combined with the surface layer in a hot-pressing manner.
Preferably, the flame-retardant layer is composed of the following raw materials in parts by weight: 30-50 parts of polypropylene staple fibers, 20-30 parts of three-dimensional hollow staple fibers and 10-20 parts of high-performance flame-retardant staple fibers. More preferably, the flame-retardant layer is prepared from the following raw materials in parts by weight: 40 parts of polypropylene staple fibers, 25 parts of three-dimensional hollow staple fibers and 15 parts of high-performance flame-retardant staple fibers.
Preferably, the reinforcing layer is composed of the following raw materials in parts by weight: 30-50 parts of polypropylene short fibers, 10-20 parts of carbon fiber short fibers and 20-30 parts of three-dimensional hollow short fibers. More preferably, the reinforcing layer is composed of the following raw materials in parts by weight: 40 parts of polypropylene staple fibers, 15 parts of carbon fiber staple fibers and 25 parts of three-dimensional hollow staple fibers.
Preferably, the length of the polypropylene staple fiber is 0.5-1 cm, and the fineness of the polypropylene staple fiber is 1.5-20D; the length of the three-dimensional hollow short fiber is 5-6.5 cm, and the fineness of the three-dimensional hollow short fiber is 1.5-20D.
Preferably, the length of the high-performance flame-retardant short fiber is 5-6.5 cm, and the fineness of the high-performance flame-retardant short fiber is 1.5-20D.
Preferably, the length of the carbon fiber is 5-6.5 cm, and the fineness of the carbon fiber is 1-12K.
Preferably, the needle-punched non-woven fabric layer is formed by needling a first flame-retardant layer, a second flame-retardant layer and a reinforcing layer positioned between the first flame-retardant layer and the second flame-retardant layer.
Preferably, the total weight ratio of the flame-retardant layer to the reinforcing layer is 1: 1-2: 1.
Preferably, the composite board is composed of a facing layer and a needle-punched non-woven fabric layer.
Preferably, the composite board is composed of two facing layers and a needle-punched non-woven fabric layer located between the two facing layers.
Preferably, the facing layer is made of polypropylene nonwoven fabric.
The second aspect of the utility model provides a preparation method of acupuncture non-woven fabrics composite sheet for plaque in the aircraft, including following step:
(1) opening and mixing the polypropylene staple fibers, the three-dimensional hollow staple fibers and the high-performance flame-retardant staple fibers weighed according to the weight, carding into net-shaped cotton wadding, and paving into a cotton wadding to obtain a flame-retardant layer;
(2) opening and mixing the polypropylene staple fibers, the three-dimensional hollow staple fibers and the carbon fiber staple fibers weighed according to the weight, carding into reticular cotton wadding, and paving into a cotton wadding to obtain a reinforcing layer;
(3) combining the flame-retardant layer obtained in the step (1) with the reinforcing layer obtained in the step (2) and then obtaining a needle-punched non-woven fabric layer through needle punching;
(4) and combining the needled non-woven fabric layer with the cover layer, preheating, putting into a preheated mold, hot-pressing the mold, taking out, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite plate for the interior trim panel of the airplane.
Preferably, the needling process is carried out by four needling machines; the needle frequency of the four-path needle machine is as follows in sequence: 640RPM, 680RPM, 700RPM and 730RPM, the needling depth is as follows: 0.9mm, 0.5mm and 0.5 mm.
Preferably, the preheating temperature of the combination of the needle-punched non-woven fabric layer and the cover layer is 130-160 ℃, and the preheating time is 10-20 min; the hot pressing temperature is 130-160 ℃, and the pressure is 0.2-0.5 MPa.
The third aspect of the utility model provides the use of acupuncture non-woven fabrics composite sheet in the preparation plaque in the aircraft.
The fourth aspect of the present invention provides a method for manufacturing an interior trim panel of an aircraft from a needled nonwoven fabric composite board, the method comprising: and (3) bonding the needle-punched non-woven fabric composite board with the surface layer facing outwards to the two sides of the non-metal honeycomb core by using a bonding agent, and cutting the composite board orderly to obtain the aircraft interior trim panel.
The utility model has the advantages that:
1. the needle-punched non-woven fabric composite board has good air permeability, and can improve the comfort level of passengers when being used for the interior decoration of an airplane;
2. the needle-punched non-woven fabric composite board has good sound absorption and heat insulation performance, can reduce the noise in the cabin and keep the temperature of the cabin at an appropriate temperature when being used for the interior decoration of the airplane;
3. the needle-punched non-woven fabric composite board of the utility model contains high-performance flame-retardant fibers, so that the flame-retardant effect is good, and the safety of the cabin can be improved when the needle-punched non-woven fabric composite board is used for the interior decoration of an airplane;
4. the utility model discloses a acupuncture non-woven fabrics composite sheet contains the carbon fiber of high modulus high strength, has improved the intensity of composite sheet greatly.
Drawings
FIG. 1 is a structural diagram of a needle-punched non-woven fabric composite board for an interior trim panel of an aircraft;
FIG. 2 is a flow chart of the production process.
Shown in the figure: 1. a sealing surface layer, 2, a flame retardant layer, 3 and a reinforcing layer.
Detailed Description
It should be noted that the following detailed description is exemplary and is intended to provide further explanation of the disclosure. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs.
As mentioned in the background art, a needled non-woven fabric composite board which has good air permeability, sound absorption and heat insulation, flame retardant effect, high strength and light weight is needed at present. Based on the structure, the utility model provides a needle-punched non-woven fabric composite board for an aircraft interior trim panel, which comprises at least one surface covering layer and a needle-punched non-woven fabric layer bonded with the surface covering layer; the needle-punched non-woven fabric layer is formed by needle punching a flame-retardant layer and a reinforcing layer; and the flame-retardant layer is combined with the surface layer in a hot-pressing manner.
The front cover layer is made of polypropylene non-woven fabric. The polypropylene non-woven fabric is prepared by the following method:
the polypropylene raw materials which are well mixed and stirred are pumped to a screw rod through a feeding system in vacuum for extrusion and melting, the melting temperature of the screw rod is 180-270 ℃, and a hot melt is obtained; filtering, metering and distributing the hot melt at 230-250 ℃ and under the pressure of 5-10 MPa; spinning the hot melt which is distributed and metered, and cooling the spun filaments by side cold air to obtain primary filaments (the hot melt which is distributed and metered is spun through a jet nozzle with the aperture of 0.3-0.8 mm, and is cooled by a cooling air box, the temperature of the cooling air box is 10-20 ℃, the speed of the cooling air is 0.2-1.5 m/s, and the filaments are cooled to obtain the primary filaments); drafting the as-grown filaments to obtain fibers; dividing and lapping the fibers to form a fiber web; hot rolling the fiber web, conveying the fiber web to a hot rolling mill through a net curtain forming roller under the driving of the net curtain forming roller, and obtaining the polypropylene non-woven fabric through the hot pressing and bonding action of an upper roller and a lower roller of the hot rolling mill, wherein the temperature of the hot rolling mill is 80-120 ℃, and the linear pressure of the hot rolling mill is 30-70 MPa; a nonwoven fabric was obtained. Wherein the surface density of the polypropylene non-woven fabric is 50-100 g/cm2The thickness is 0.1 to 0.5 mm. The sealing layer is made of polypropylene non-woven fabrics, so that the surface of the plate obtained after hot press molding is smooth, and the post-production of the interior trimming panel is facilitated.
The total weight ratio of the flame-retardant layer to the reinforcing layer is 1: 1-2: 1. The composite board is composed of a sealing layer and a needle-punched non-woven fabric layer. The composite board is composed of two facing layers and a needle-punched non-woven fabric layer positioned between the two facing layers. One preferred combination of needle-punched nonwoven is: the flame-retardant fabric is formed by needling a first flame-retardant layer, a second flame-retardant layer and a reinforcing layer positioned between the first flame-retardant layer and the second flame-retardant layer. The flame-retardant fabric can also be formed by combining a flame-retardant layer and a reinforcing layer and then needling the flame-retardant layer and the reinforcing layer. But the total weight ratio of the flame-retardant layer to the reinforcing layer is 1: 1-2: 1. The weight of the first flame retardant layer and the second flame retardant layer may be different or the same while maintaining the total weight ratio.
The flame-retardant layer is composed of the following raw materials in parts by weight: 30-50 parts of polypropylene staple fibers, 20-30 parts of three-dimensional hollow staple fibers and 10-20 parts of high-performance flame-retardant staple fibers. More preferably, the flame-retardant layer is prepared from the following raw materials in parts by weight: 40 parts of polypropylene staple fibers, 25 parts of three-dimensional hollow staple fibers and 15 parts of high-performance flame-retardant staple fibers.
The reinforced layer is composed of the following raw materials in parts by weight: 30-50 parts of polypropylene short fibers, 10-20 parts of carbon fiber short fibers and 20-30 parts of three-dimensional hollow short fibers. More preferably, the reinforcing layer is composed of the following raw materials in parts by weight: 40 parts of polypropylene staple fibers, 15 parts of carbon fiber staple fibers and 25 parts of three-dimensional hollow staple fibers.
The length of the polypropylene staple fiber is 0.5-1 cm, and the fineness of the polypropylene staple fiber is 1.5-20D; the length of the three-dimensional hollow short fiber is 5-6.5 cm, and the fineness of the three-dimensional hollow short fiber is 1.5-20D.
The length of the high-performance flame-retardant short fiber is 5-6.5 cm, and the fineness of the high-performance flame-retardant short fiber is 1.5-20D.
The length of the carbon fiber is 5-6.5 cm, and the fineness of the carbon fiber is 1-12K.
In the needle non-woven fabric, the polypropylene fiber has a low melting point, generally about 130-160 ℃. And the polypropylene fiber has good strength, good elasticity and wear resistance, and can improve the strength and wear resistance of the needled non-woven fabric composite board. In order to enable the bonding effect of the polypropylene fibers to be better, the staple fibers with the fiber length of 0.5-1 cm are selected, so that the polypropylene staple fibers can be better dispersed in other fibers during cotton mixing and can be bonded with more fibers during hot-press molding. Meanwhile, the length of the polypropylene short fiber is reduced, the porosity between the fibers can be increased when the polypropylene short fiber is mixed with other fibers and is paved, and the sound absorption and heat insulation effects can be improved after the polypropylene short fiber is formed. In order to ensure the pores of the product and the flatness of the surface of the composite board, the other fibers are preferably short fibers with the length of 5-6.5 cm.
The three-dimensional hollow fiber is chemical fiber with a thin tubular cavity in the axial direction of the fiber, and has good elasticity, the cavity in the fiber can improve the heat insulation performance of a product by using the three-dimensional hollow short fiber, and the good elasticity can still maintain the porosity among the fibers after the product is hot-pressed, so that the good sound absorption and heat insulation effects can still be maintained after the product is hot-pressed.
High performance flame retardant fibers are fibers that merely smolder in a flame, leaving the flame, and the smolder self-extinguishes. Compared with common fibers, the flame-retardant fibers have obviously reduced flammability, obviously slowed combustion rate in the combustion process, quick self-extinguishment after leaving a fire source and less release of toxic smoke. The fiber and the textile have the effects of flame retardance, heat insulation and molten drop resistance, and the application performance, the safety performance and the added value of the fiber and the textile are greatly improved. The fiber can improve the flame-retardant and heat-insulating effects of the product.
The high-performance flame-retardant fiber and the three-dimensional hollow fiber are arranged on two sides of the needled non-woven fabric, so that the flame retardance can be effectively realized, and the porosity and the heat-insulating property of the product can be simultaneously maintained. Polypropylene serves to bind the two fibers and has some strength and elasticity.
The carbon fiber is a high-strength high-modulus fiber with the carbon content of more than 90 percent, and the high-temperature resistant fiber is the first of all chemical fibers. The carbon fibers have a low density and thus a high specific strength and a high specific modulus. The carbon fibers are arranged in the middle layer (reinforcing layer) of the needle-punched non-woven fabric, so that the mechanical strength of the product can be effectively improved, and the composite board plays a supporting role; while the three-dimensional hollow fibers can maintain the porosity and thermal insulation properties of the reinforcing layer. Polypropylene serves to bind the two fibers. In order to ensure the pores of the product and the flatness of the surface of the composite board, the short fibers with the length of 5-6.5 cm are preferably selected for other fibers except the polypropylene fibers, and the fineness of the fibers is kept consistent and is preferably 1.5-20D.
The utility model also provides a preparation method of acupuncture non-woven fabrics composite sheet for plaque in the aircraft, including following step:
(1) opening and mixing the polypropylene staple fibers, the three-dimensional hollow staple fibers and the high-performance flame-retardant staple fibers weighed according to the weight, carding into net-shaped cotton wadding, and paving into a cotton wadding to obtain a flame-retardant layer;
(2) opening and mixing the polypropylene staple fibers, the three-dimensional hollow staple fibers and the carbon fiber staple fibers weighed according to the weight, carding into reticular cotton wadding, and paving into a cotton wadding to obtain a reinforcing layer;
(3) combining the flame-retardant layer obtained in the step (1) with the reinforcing layer obtained in the step (2) and then obtaining a needle-punched non-woven fabric layer through needle punching;
(4) and combining the needled non-woven fabric layer with the cover layer, preheating, putting into a preheated mold, hot-pressing the mold, taking out, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite plate for the interior trim panel of the airplane.
The needling process is carried out by four needling machines; the needle frequency of the four-path needle machine is as follows in sequence: 640RPM, 680RPM, 700RPM and 730RPM, the needling depth is as follows: 0.9mm, 0.5mm and 0.5 mm.
The preheating temperature of the combination of the needle-punched non-woven fabric layer and the cover layer is 130-160 ℃, and the preheating time is 10-20 min; the hot pressing temperature is 130-160 ℃, and the pressure is 0.2-0.5 MPa.
The materials need to be preheated before hot pressing, so that the problem that the polypropylene fibers are not melted during hot pressing and hot pressing is finished, the bonding effect of the materials is poor, and the materials are easy to peel off is solved. Therefore, the needle-punched non-woven fabric is preheated before hot pressing, and the preheating temperature is consistent with the hot pressing temperature. And (4) obtaining the composite board after hot press molding, cooling to room temperature, and demolding. And brushing a layer of silicone oil release agent on the mold before preheating the mold so as not to make the material stick on the mold during demolding.
In order to clearly illustrate the technical features of the present solution, the present solution is explained below by way of specific embodiments.
Example 1
(1) 50Kg of polypropylene staple fiber, 30Kg of three-dimensional hollow staple fiber and 20Kg of high-performance flame-retardant staple fiber are weighed by automatic weighing equipment and then are loosened and mixed; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a flame-retardant layer in a circulating swinging lapping mode;
(2) 50Kg of polypropylene staple fibers, 15Kg of carbon fiber staple fibers and 30Kg of three-dimensional hollow staple fibers are prepared into a cotton wadding which is a reinforcing layer according to the method in the step (1);
(3) placing the flame-retardant layer obtained in the step (1) above the reinforcing layer obtained in the step (2) to obtain a fiber web layer, and sequentially needling the fiber web layer by four needle machines to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating at 130 ℃ for 20min, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 20s, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
Example 2
(1) Weighing 33Kg of polypropylene staple fibers, 20Kg of three-dimensional hollow staple fibers and 10Kg of high-performance flame-retardant staple fibers by automatic weighing equipment, and then opening and mixing cotton; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a first flame-retardant layer in a circulating swinging lapping mode; weighing 33Kg of polypropylene staple fibers, 20Kg of three-dimensional hollow staple fibers and 10Kg of high-performance flame-retardant staple fibers by automatic weighing equipment, and then opening and mixing cotton; carding into netted wadding by a carding machine, and laying into a cotton wadding in a circulating swinging lapping mode to obtain a second flame-retardant layer
(2) Preparing 33Kg of polypropylene staple fibers, 15Kg of carbon fiber staple fibers and 20Kg of three-dimensional hollow staple fibers into a cotton wadding which is a reinforcing layer according to the method in the step (1);
(3) clamping the reinforcing layer obtained in the step (2) and the first flame-retardant layer and the second flame-retardant layer obtained in the step (1) to obtain a fiber mesh layer, and needling the fiber mesh layer through four needle machines in sequence to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating for 15min at 160 ℃, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 15s, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
Example 3
(1) Weighing 25Kg of polypropylene staple fiber, 15Kg of three-dimensional hollow staple fiber and 10Kg of high-performance flame-retardant staple fiber by automatic weighing equipment, and then opening and mixing cotton; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a first flame-retardant layer in a circulating swinging lapping mode; weighing 25Kg of polypropylene staple fiber, 15Kg of three-dimensional hollow staple fiber and 10Kg of high-performance flame-retardant staple fiber by automatic weighing equipment, and then opening and mixing cotton; and carding the cotton into netted wadding by a carding machine, and paving the netted wadding into a cotton wadding in a circulating swinging lapping mode, wherein the cotton wadding is the second flame-retardant layer.
(2) 50Kg of polypropylene staple fibers, 15Kg of carbon fiber staple fibers and 30Kg of three-dimensional hollow staple fibers are prepared into a cotton wadding which is a reinforcing layer according to the method in the step (1);
(3) clamping the reinforcing layer obtained in the step (2) and the first flame-retardant layer and the second flame-retardant layer obtained in the step (1) to obtain a fiber mesh layer, and sequentially needling the fiber mesh layer by four needling machines to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating at 145 ℃ for 20min, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 10s and cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
Example 4
(1) Weighing 40Kg of polypropylene staple fibers, 26Kg of three-dimensional hollow staple fibers and 13Kg of high-performance flame-retardant staple fibers by automatic weighing equipment, and then opening and mixing cotton; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a first flame-retardant layer in a circulating swinging lapping mode; weighing 20Kg of polypropylene staple fibers, 13Kg of three-dimensional hollow staple fibers and 6Kg of high-performance flame-retardant staple fibers by automatic weighing equipment, and then opening and mixing cotton; and carding the cotton into netted wadding by a carding machine, and paving the netted wadding into a cotton wadding in a circulating swinging lapping mode, wherein the cotton wadding is the second flame-retardant layer.
(2) 40Kg of polypropylene short fiber, 15Kg of carbon fiber short fiber and 25Kg of three-dimensional hollow short fiber are made into a cotton wadding which is a reinforcing layer according to the method in the step (1);
(3) clamping the reinforcing layer obtained in the step (2) and the first flame-retardant layer and the second flame-retardant layer obtained in the step (1) to obtain a fiber mesh layer, and needling the fiber mesh layer through four needle machines in sequence to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating at 145 ℃ for 20min, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 10s and cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
Comparative example 1
(1) 60Kg of polypropylene staple fibers and 40Kg of high-performance flame-retardant staple fibers are weighed by automatic weighing equipment and then are subjected to opening and cotton mixing; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a flame-retardant layer in a circulating swinging lapping mode;
(2) 60Kg of polypropylene staple fibers and 35Kg of carbon fiber staple fibers are manufactured into a cotton wadding, namely a reinforcing layer, according to the method in the step (1);
(3) placing the flame-retardant layer obtained in the step (1) above the reinforcing layer obtained in the step (2) to obtain a fiber web layer, and sequentially needling the fiber web layer by four needle machines to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating for 15min at 160 ℃, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 15s, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
Comparative example 2
(1) 50Kg of polypropylene staple fibers and 15Kg of three-dimensional hollow staple fibers are weighed by automatic weighing equipment and then are loosened and mixed; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a first flame-retardant layer in a circulating swinging lapping mode; 50Kg of polypropylene staple fibers and 15Kg of three-dimensional hollow staple fibers are weighed by automatic weighing equipment and then are loosened and mixed; and carding the cotton into netted wadding by a carding machine, and paving the netted wadding into a cotton wadding in a circulating swinging lapping mode, wherein the cotton wadding is the second flame-retardant layer.
(2) 50Kg of polypropylene staple fibers and 15Kg of three-dimensional hollow staple fibers are made into a cotton wadding, namely a reinforcing layer, according to the method in the step (1);
(3) clamping the reinforcing layer obtained in the step (2) between the first flame-retardant layer and the second flame-retardant layer obtained in the step (1) to obtain a fiber web layer, and sequentially needling the fiber web layer by four needle machines to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating for 15min at 160 ℃, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 15s, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
Comparative example 3
(1) Weighing 20Kg of polypropylene staple fibers, 25Kg of three-dimensional hollow staple fibers and 20Kg of high-performance flame-retardant staple fibers by automatic weighing equipment, and then opening and mixing cotton; carding into netted wadding by a carding machine, and laying into a cotton wadding which is a first flame-retardant layer in a circulating swinging lapping mode; weighing 20Kg of polypropylene staple fibers, 25Kg of three-dimensional hollow staple fibers and 20Kg of high-performance flame-retardant staple fibers by automatic weighing equipment, and then opening and mixing cotton; and carding the cotton into netted wadding by a carding machine, and paving the netted wadding into a cotton wadding in a circulating swinging lapping mode, wherein the cotton wadding is the second flame-retardant layer.
(2) Preparing 20Kg of polypropylene staple fibers, 20Kg of carbon fiber staple fibers and 25Kg of three-dimensional hollow staple fibers into a cotton wadding which is a reinforcing layer according to the method in the step (1);
(3) clamping the reinforcing layer obtained in the step (2) between the first flame-retardant layer and the second flame-retardant layer obtained in the step (1) to obtain a fiber web layer, and sequentially needling the fiber web layer by four needle machines to obtain a felting needle non-woven fabric; the needle frequency of the four needle machines is as follows: 640RPM, 680RPM, 700RPM, and 730RPM, the penetration depth is: 0.9mm, 0.5mm and 0.5mm, input speed: 1.16, 2.18, 2.16 and 2.27m/min, and the output speed is as follows: 2.01, 2.18, 2.16 and 2.27 m/min.
(4) And (3) clamping the needled non-woven fabric between the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer together into a hot oven for preheating for 15min at 160 ℃, taking out the first surface covering layer and the second surface covering layer, then putting the first surface covering layer and the second surface covering layer into a pre-preheated mold, putting the mold into a flat press for hot pressing, taking out the mold after 15s, cooling to room temperature, and demolding to obtain the needled non-woven fabric composite board for the aircraft interior trim panel.
In the above examples and comparative examples: the needle-punched non-woven fabric in example 1 was a combination of a flame retardant layer and a reinforcing layer, the total weight ratio of the flame retardant layer to the reinforcing layer being 1: 1; the needle-punched non-woven fabric in example 2 is a combination of two flame retardant layers sandwiching a reinforcing layer, the weight of the two flame retardant layers is the same, and the total weight ratio of the flame retardant layer to the reinforcing layer is 2: 1; the needle-punched non-woven fabric in example 3 is a combination of two flame retardant layers sandwiching a reinforcing layer, the weight of the two flame retardant layers is the same, and the total weight ratio of the flame retardant layer to the reinforcing layer is 1: 1; the needle-punched non-woven fabric in example 4 was a combination of two flame retardant layers sandwiching a reinforcing layer, the weight of the first flame retardant layer was 2 times that of the second flame retardant layer, and the total weight ratio of the flame retardant layer to the reinforcing layer was 1.5: 1; the needle-punched non-woven fabric in comparative example 1 was a combination in which the hollow fibers were removed; the needle-punched non-woven fabric in comparative example 2 was a combination from which the flame retardant fibers and carbon fibers were removed; the needle-punched non-woven fabric in comparative example 3 is a combination of polypropylene fiber in an amount reduced by half; the comparative examples were used to examine the effect of these several fibers in needle punched nonwovens.
The composite panels prepared in examples 1 to 4 and comparative examples 1 to 3 were subjected to thickness and areal density measurements (areal density ═ weight of composite panel/area of composite panel) and the data obtained are shown in table 1.
TABLE 1 thickness and areal Density
The weight of the fibers used in examples 1 to 4 and comparative examples 1 to 3 was substantially the same, and the thickness and surface density of the resulting needled nonwoven composite board were also not substantially different.
Test example 1 mechanical property test
Tensile strength tests and peel strength tests were performed on the composite boards prepared in examples 1 to 4 and comparative examples 1 to 3 using a DR028-1000 type universal electronic tensile machine, and the results are shown in table 2.
Wherein the peel strength is the peel force/specimen thickness
Test example 2 Heat insulation Performance test
The composite panels prepared in examples 1 to 4 and comparative examples 1 to 3 were subjected to a thermal conductivity test using a labteach quicklinie-10 type thermal conductivity meter, and the results are shown in table 2.
Test example 3 flame retardancy test
The results of the oxygen index test of the composite sheets prepared in examples 1 to 3 and comparative examples 1 to 3 using the JF-3 type oxygen index instrument are shown in Table 2
Test example 4 air permeability test
The composite panels prepared in examples 1 to 4 and comparative examples 1 to 3 were tested for air permeability using a model YG461D digital air permeameter, the results of which are shown in Table 2.
Test example 5 impact test
The composite boards prepared in examples 1 to 4 and comparative examples 1 to 3 were subjected to an impact performance test using an XJU-22J cantilever beam impact tester, and the results are shown in table 2.
TABLE 2 test results of test examples 1 to 5
As can be seen from table 2, the tensile strength of the composite board can be increased with increasing the amount of the carbon fibers (examples 1 to 4 and comparative example 1), but the increase ratio is not large, and the amount of the carbon fibers is controlled to be about 15 parts in order to control the cost of the composite board.
The peel strength increases with the increase of the polypropylene consumption, and when the polypropylene consumption is reduced by half (examples 1-4 and comparative example 3), the obtained composite board has poor bonding effect, and is easy to peel from a place with poor bonding, so that the use of the product is influenced. The polypropylene is added in an amount of at least half the total fiber addition.
The coefficient of heat conductivity increases along with the hollow fiber quantity, but its coefficient of heat conductivity of the content that increases hollow fiber alone is higher than the utility model discloses the coefficient of heat conductivity of the composite sheet that makes (embodiment 1 ~ 4 and comparative example 3), explain that although hollow fiber can increase thermal-insulated effect but need use with carbon fiber, polypropylene fiber cooperation can reach the optimal value.
The oxygen index is increased along with the increase of the using amount of the high-performance flame-retardant fibers, the more the using amount of the flame-retardant fibers is, the higher the oxygen index is (examples 1-4 and comparative examples 2 and 3), but the cost of the flame-retardant fibers is higher, and the oxygen index can reach more than 40%, so that the use requirement of the product can be met.
Generally, the lower the areal density the better the air permeability of the product, but this is also related to the number of voids between the fibers, with larger voids giving better air permeability of the product. The gas permeability difference between the composite sheet that embodiment 1 ~ 4 prepared is not big, and is visible the utility model discloses the fibre that uses can fine cooperation, and the hole between the fibre is also more.
The impact strength is related to the elastic modulus of the product, and it can be seen from table 2 that the addition of carbon fibers and three-dimensional hollow fibers can increase the impact strength of the product.
In summary, the product properties obtained in example 2 and example 3 were the best. The needle-punched non-woven fabrics in the embodiment 2 and the embodiment 3 are all of a combined structure of a first flame-retardant layer, a reinforcing layer and a second flame-retardant layer, and the fiber dosage of the first flame-retardant layer and the second flame-retardant layer is the same. So the acupuncture non-woven fabrics is the fibre quantity looks isostructure of first fire-retardant layer, enhancement layer and the fire-retardant layer combination of second and first fire-retardant layer and the fire-retardant layer of second does the utility model discloses an optimal structure. The weight ratio of the flame retardant layer to the reinforcing layer in example 2 was 2:1, and the weight ratio of the flame retardant layer to the reinforcing layer in example 3 was 1: 1. The products prepared in the embodiments 2 and 3 can meet the flame retardant requirement, have good heat insulation, sound absorption and air permeability, and are light in weight, thus being ideal composite boards required by the interior trim panels of the airplanes.
Of course, the above description is not limited to the above examples, and technical features of the present invention that are not described in the present application may be implemented by or using the prior art, and are not described herein again; the above embodiments and drawings are only used for illustrating the technical solutions of the present invention and are not intended to limit the present invention, and the present invention has been described in detail with reference to the preferred embodiments, and those skilled in the art should understand that changes, modifications, additions or substitutions made by those skilled in the art within the spirit of the present invention should also belong to the protection scope of the claims of the present invention.
Claims (6)
1. The needled non-woven composite board for the aircraft interior trim panel is characterized by comprising at least one surface covering layer and a needled non-woven fabric layer which is hot-pressed with the surface covering layer; the needle-punched non-woven fabric layer is formed by needle-punching a flame-retardant layer and a reinforcing layer, and the flame-retardant layer is combined with the sealing surface layer in a hot-pressing mode.
2. The needled nonwoven composite board of claim 1 wherein said composite board is comprised of a facing layer and a needled nonwoven layer.
3. The needled nonwoven composite board of claim 1 wherein said composite board is comprised of a first facing layer, a second facing layer, and a needled nonwoven layer disposed between the first facing layer and the second facing layer.
4. The needled nonwoven composite board of claim 1 wherein the needled nonwoven layer is comprised of a first flame retardant layer, a second flame retardant layer, and a reinforcing layer disposed between the first flame retardant layer and the second flame retardant layer.
5. The needled nonwoven composite board of claim 1 wherein said needled nonwoven layer is comprised of a flame retardant layer and a reinforcing layer.
6. The needled non-woven composite board according to claim 1, wherein the total weight ratio of the flame retardant layer to the reinforcing layer is 1:1 to 2: 1.
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